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Modal analysis only gives modes and frequencies, normally evaluated between 50 and 2000Hz in aerospace applications. This doesn’t give stresses; the difficult task is then to drive the solved system using the dynamics module and to excite the structure, using effective mass and mode participations and effective mass @ resonances to determine which frequencies will be a problem. You may then need to stiffen your structure and re-evaluate. If you have a top end package, you can add rotational stresses, so you get mode + rotation. You should be able to apply sine or PSD or other functions, depending on your requirements and solve, but this is when it gets difficult.
Once you excite your structure, you can evaluate nodal displacements with respect to input locations by function and see what your modal deformations may be. Don’t forget to apply damping because this makes a difference. Then compare your findings to real life test bed
God luck to all you FEA guys ....